CFD validation of a supersonic laminar flow control conceptA three-dimensional Navier-Stokes code is used in conjunction with a linear compressible stability analysis code to develop a numerical procedure for prediction of laminar flow transition. The procedure is applied to a modified F-16XL fighter with a laminar flow control glove at supersonic speed. Details of boundary layer stability analysis indicate that, computationally, laminar flow could be realized on the highly swept wing in the absence of the leading edge attachment-line contamination. Effects of the three-dimensionality of the flow were shown to be important in the boundary layer stability analysis. The numerically predicted surface pressures compare favorably with the flight test data.
Document ID
19910034548
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Woan, Chung-Jin (Rockwell International Corp. Los Angeles, CA, United States)
Gingrich, Philip B. (Rockwell International Corp. Los Angeles, CA, United States)
George, Michael W. (Rockwell International Corp. Los Angeles, CA, United States)